flux diverngence in simulating nasa rotor 67 using foam extend
 

hi
I hope you are well.
I'm simulating nasa Rotor67 in foam-extend using steadyCompresibleMRF solver.
after 7000 iteration , all of results converge to experimental design point , but max of flux divergence is still high and mach number is 0.1 higher than desgin point ( desgin point =1.38).
1- Is the flux diverngence important parameter to valdiate convergence?
2-how can I fix this parameter?
3- Do you have any idea to reduce the mach number ?
Attachment 77653

Hi, I am trying to simulate Rotor 67 in foam-extend, too. Can you help me about the boundary condition?